I'm making a fuselage from 2 former Naish carbon bars and wonder what angle of attacks should be for front wing and stab relative to fuselage. Delta hydrofoil video says the angle between wing and stab is the best around 3 degrees, but how does this number is split between each wing and the fuselage? I assume the fuselage moving below the water surface at an angle would create more drag than necessary.
The two wing sets I'm planning to use are
1. LF Rocket
2. JNJ (from aliexpress)
LF Rocket setup is no brainer, because their aluminum fuselage is a plane surface. Therefore, I just mount LF wings as they were in the original LF setup. On the other hand, JNJ is trickier because the fuse is curved. I've measured AoA for the front wing and was surprised to see that it is negative 1.5 degrees! My expectation is for the front wing be at zero (or perhaps slightly positive) angle relative to the fuselage, thus providing the lift, and stabilizer being at 0 degrees. This idea is consistent with what I have measured for LF Rocket: 0 degrees for the front wing and 0 degrees for the stab. On the other hand, everybody says that stab provides negative lift (and therefore must be at negative angle). Therefore, to repeat my question, what are the canonical numbers for the front wing and stab AoA (relative to the fuselage)?